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Impact-Time-Control Guidance Law With Constraints on Seeker Look Angle

机译：搜寻者视角受限的冲击时间控制制导律

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摘要

An impact-time-control guidance (ITCG) law is required for simultaneous attack of multiple missiles. In application of ITCG, the limit of seeker look angle should be regarded as an important factor in homing engagement scenarios. To avoid the loss of target tracking during engagement, the seeker's look angle should be confined to the seeker's field-of-view limit. This paper suggests a new ITCG law for a realistic situation with constraints on seeker look angle driven by the exact nonlinear equations of motion in plane. The proposed guidance law ensures the seeker's look angle to reduce monotonically from the initial value to zero at the intercept point. The resulting solution is presented in the form of proportional navigation guidance law with a time-varying navigation gain. The closed-form navigation gain can be obtained from information on the current missile-to-target range and heading angle.
机译：同时攻击多枚导弹需要有撞击时间控制制导（ITCG）法。在ITCG的应用中，导引头视角的限制应被认为是制导交战场景的重要因素。为了避免在啮合过程中失去目标跟踪，应该将搜寻器的视角限制在搜寻器的视野范围内。本文提出了一种适用于现实情况的新ITCG定律，该定律受平面中精确的非线性运动方程驱动的对导引器视角的限制。拟议的制导律可确保搜寻器的视角在拦截点处从初始值单调减小到零。所得解决方案以比例导航制导律的形式给出，并具有随时间变化的导航增益。可以从有关当前导弹到目标的范围和航向角的信息获得封闭形式的导航增益。

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